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EP0600699A1 - Récepteur mobile pour signaux satellites radio diffusés - Google Patents

Récepteur mobile pour signaux satellites radio diffusés Download PDF

Info

Publication number
EP0600699A1
EP0600699A1 EP93309519A EP93309519A EP0600699A1 EP 0600699 A1 EP0600699 A1 EP 0600699A1 EP 93309519 A EP93309519 A EP 93309519A EP 93309519 A EP93309519 A EP 93309519A EP 0600699 A1 EP0600699 A1 EP 0600699A1
Authority
EP
European Patent Office
Prior art keywords
antenna
aeroplane
radome
directive
antennas
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP93309519A
Other languages
German (de)
English (en)
Other versions
EP0600699B1 (fr
Inventor
Noboru c/o Nippon Hoso Kyokai Toyama
Masaru C/O Nippon Hoso Kyokai Fujita
Osamu Ono
Hisaji Nakamura
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Japan Broadcasting Corp
ANA Holdings Inc
Original Assignee
Nippon Hoso Kyokai NHK
All Nippon Airways Co Ltd
Japan Broadcasting Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from JP4320445A external-priority patent/JPH06169274A/ja
Priority claimed from JP32044492A external-priority patent/JP3306758B2/ja
Application filed by Nippon Hoso Kyokai NHK, All Nippon Airways Co Ltd, Japan Broadcasting Corp filed Critical Nippon Hoso Kyokai NHK
Publication of EP0600699A1 publication Critical patent/EP0600699A1/fr
Application granted granted Critical
Publication of EP0600699B1 publication Critical patent/EP0600699B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H01Q3/24—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the orientation by switching energy from one active radiating element to another, e.g. for beam switching
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/32—Adaptation for use in or on road or rail vehicles
    • H01Q1/325—Adaptation for use in or on road or rail vehicles characterised by the location of the antenna on the vehicle
    • H01Q1/3275—Adaptation for use in or on road or rail vehicles characterised by the location of the antenna on the vehicle mounted on a horizontal surface of the vehicle, e.g. on roof, hood, trunk
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H01Q3/02—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/185—Space-based or airborne stations; Stations for satellite systems
    • H04B7/18502—Airborne stations
    • H04B7/18506—Communications with or from aircraft, i.e. aeronautical mobile service
    • H04B7/18508—Communications with or from aircraft, i.e. aeronautical mobile service with satellite system used as relay, i.e. aeronautical mobile satellite service
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/185—Space-based or airborne stations; Stations for satellite systems
    • H04B7/1853—Satellite systems for providing telephony service to a mobile station, i.e. mobile satellite service
    • H04B7/18569—Arrangements for system physical machines management, i.e. for construction operations control, administration, maintenance
    • H04B7/18571—Arrangements for system physical machines management, i.e. for construction operations control, administration, maintenance for satellites; for fixed or mobile stations

Definitions

  • the present invention relates to a mobile receiver for satellite broadcast which can receive an electromagnetic wave of the satellite broadcast during flight.
  • An apparatus for receiving image information of a satellite broadcast during moving has been developed or in an experimental stage for those for train, ship, bus and small car.
  • the prior art apparatus since a plurality of antennas on a flat plate are directed to a broadcasting satellite by using outputs of tracking sensors attached to the plate, the same number of tracking circuits as the number of divisions of the apparatus are required when the apparatus is divided.
  • a different technical requirement is imposed to an apparatus that is composed of several subdivided apparatuses, for receiving image information of the satellite broadcast during the flight of an aeroplane.
  • the prior art tracking system in the apparatus is a mechanical tracking system or a combination of the mechanical tracking system and an electronic tracking system, and a total electronic tracking system has not yet been developed.
  • a mobile receiver for satellite broadcast comprising: directive antenna means; a navigation unit for generating a navigation signal representing a position and an attitude of an aeroplane; control means for generating a control signal for controlling the antenna means, on the basis of the navigation signal from the navigation unit and prestored information indicating a position of a broadcasting satellite; and drive means for driving the antenna means in response to the antenna control signal from the control means to orient directive directions of the antenna means toward the broadcasting satellite.
  • a mobile receiver for satellite broadcast comprising: directions antenna means including a plurality of antenna arranged in a radome with different antenna orientations to cover all azimuths; a navigation unit for generating a navigation signal representing a position and an attitude of an aeroplane; control means for generating an antenna control signal to select antennas to be used for receiving the electromagnetic wave, on the basis of the navigation signal the data of the navigation unit; and composition means for selecting the antenna means in response to the antenna control signal from the control means and for in-phase composing signals received by the selected directive antenna means.
  • the present mobile receiver for satellite broadcast comprises a radome 1 made of FRP, directive antennas 3 such as array antennas, phased antennas or parabola antennas, an inertial navigator 5 which outputs navigation data during flight, a control unit 7 for obtaining a control signal for controlling a directive directions of the antennas 3, on the basis of the navigation data, a drive unit 9 for directing the antenna toward satellite broadcast by using the control signal from the control unit 7, and a signal composition unit 11 for in-phase composing signal outputs received by the antennas 3.
  • the signal composition unit 11 in-phase composes the intermediate frequency outputs from the antennas.
  • the antennas 3 is a rectangular antenna of approximately 15 cm x approximately 40 cm, and one side of a dielectric substrate is a ground plane and the opposite side has approximately 200 radiation elements regularly arranged thereon. Since it is assumed that the present apparatus is used at a high altitude at which an air pressure falls to one quarter of that in the ground, a material of the antenna substrate is a composite rigid substrate of polyethylene and air or a composite substrate material of polytetrafluoroethylene and glass fiber, which provides a high gain and is not broken under a reduced pressure.
  • the inertial navigator 5 determines a position and an attitude of an aeroplane by an auto-inference navigation method and it generates data on the direction of travel of the aeroplane, a pitching angle, a rolling angle, an altitude, a latitude and a longitude as well as other data necessary for the navigation of the aeroplane in the form of 32-bit digital signal as defined by the AEEC (Aero-Electronic Engineering Committee).
  • a digital signal of Fig. 4 represents a current latitude of the aeroplane.
  • the bit sequences of other data are continuously outputted at a predetermined convention, and the control unit 7 first detects only the bit sequences of the data relating to the attitude, altitude and position which are necessary for the present invention.
  • the type of the information is defined by a label represented by the first 8-bit (bits 1-8) of the bit sequence.
  • the first 8 bits '11001000' represent a label 310.
  • the control unit 7 recognizes the bit sequence as latitude data. If the first 8 bits are '11001001', it represents a label 311 which is detected as latitude data. Other data are detected in a similar manner.
  • the control unit 7 detects the bit sequence of data necessary for the control of the antenna by the label and generate concrete data based on the bit sequence subsequent to bit 9. It generates a control signal to direct the antenna 3 toward the satellite broadcast by the concrete data and a process logic prestored in a ROM (read-only memory) of the control unit 7.
  • the drive unit 9 drives the antenna 3 at a pitch of 0.1 degree. Without such a precision, the electromagnetic wave of the satellite broadcast could not be received.
  • the control unit 7, the drive unit 9, the signal composition unit 11, a tuner 13 and a monitor 19 are accommodated in a fuselage of the aeroplane which is a pressurized area as shown in Fig. 1 in order to protect them from a temperature change. Only the antennas 3 are mounted externally of the fuselage and are covered with the radome 1.
  • Figs. 2 and 3 show a construction in which a plurality of divided antennas are accommodated in the radome 1 on the fuselage of the aeroplane.
  • Two antennas 3 are mounted at the front and rear of the radome 1.
  • An arrester 15 is bonded to a wall of the radome 1.
  • the arrester 15 may be an array of band-shaped or bar-shaped metals or disk-shaped metals.
  • the antennas 3 are arranged as further from the arrester 15 as possible.
  • the two antennas 3 are mounted on turn tables 17 and the rotation angle ⁇ of the turn table 17 and the angle of inclination ⁇ of the antenna 3 are controlled by the control unit 7 and the drive unit 9 shown in Fig.
  • the antennas 3 may be of any type so long as they can receive the satellite broadcast but a planar antenna is preferable in view of compactness.
  • the inside and the outside of the radome are substantially at the same temperature and hence there is a very large temperature change.
  • the material for the mechanical elements of the antenna is preferably polytetrafluoroethylene (durable temperature 260°C to -270°C) which is durable to not only a high temperature but also a low temperature.
  • Figs. 5 to 8 show results of measurement of the transmittance of the electromagnetic wave when the antennas are arranged in the radome having the arrester bonded thereto as shown in Figs. 2 and 3 and the azimuth is changed by 22.5 degrees at a time.
  • a receiving C/N ratio by one antenna not covered by the radome having the arrester bonded thereto is 11 dB.
  • the direction of the electromagnetic wave relative to the radome is oriented as shown in Fig. 9.
  • the antenna is controlled and driven to be oriented as shown in Figs. 2 and 3. This corresponds to the angle 0 degree of the measurement.
  • the tables of Figs. 5 to 8 show results of measurement of the transmittance of the electromagnetic wave when the antennas are arranged in the radome having the arrester bonded thereto as shown in Figs. 2 and 3 and the azimuth is changed by 22.5 degrees at a time.
  • a receiving C/N ratio by one antenna not covered by the radome having the arrester bonded thereto
  • the receiving C/N ratio of the antenna mounted at the front of the radome is 9.5 dB and the receiving C/N ratio of the antenna mounted at the rear is 8.75 dB.
  • the receiving C/N ratio is 1.5 dB lower than that attained when the radome is not attached because of the affect of the radome and the arrester.
  • the receiving C/N ratio is 2.25 dB lower than that attained when the radome is not attached because of the affect by the two arresters arranged between the antennas.
  • the receiving C/N ratios are different between the front mounting and the rear mounting depending on the angle of incidence of the electromagnetic wave, but when the radar charts of the antenna gains of Figs. 7 and 8 are combined, it provides an antenna gain which is uniform in substantially all directions. Namely, by combining the received signals from the two antennas, the output is substantially constant.
  • the satellite broadcast can be watched on the monitor 19.
  • Figs. 10 and 11 show a mount position of the radome on the aeroplane.
  • the present mobile receiver for the satellite broadcast comprises a radome 1 made of FRP, directive array antennas 23, an inertial navigator 5 for outputting navigation data during flight, a control unit 27 for generating a control signal to select the array antennas 23 and a signal composition unit 29 for in-phase composing the outputs of the signals received from the array antennas 23.
  • the control unit 27, the signal composition unit 29, the tuner 13 and the monitor 19 are accommodated in the fuselage of the aeroplane which is a pressurized area as shown in Fig. 12 to protect them from a temperature change. Only the array antennas 23 are mounted externally of the fuselage and are covered with the radome 1.
  • the radome 1, the inertial navigator 5, the tuner 13 and the monitor 19 which are designated by the same numerals as those of the first embodiment have been explained above and the explanation thereof is omitted here.
  • the inertial navigator 5 generates a control signal to select the array antennas 23.
  • the substrate material of the array antennas 3 is preferably same as that of the first embodiment.
  • a configuration of the aeroplane-mounted mobile receiver for the satellite broadcast is now explained. Twelve array antennas 23 are arranged in the radome 1 which is outside of the fuselage. Each array antenna 23 is divided into 6 x 4 blocks (not shown) and signals received by the array antenna 23 are in-phase composed by the in-phase composition circuit 37 after the received signals have been converted to intermediate frequency, and the in-phase composed signal is supplied to the signal composition unit 29 in the fuselage as a output of the array antenna 23.
  • the control unit 27 calculates the direction of the broadcasting satellite on the basis of the data of the inertial navigator 5 mounted in the aeroplane, determines the array antennas 23 which can currently receive the electromagnetic wave, and the control unit 27 sends a control signal to the signal composition circuit 29.
  • the signal composition unit 29 selects two or more optimum signals from the outputs of the twelve array antennas 23 on the basis of the control signal from the control unit 27 and in-phase composes them.
  • Figs. 13 and 14 show a method for mounting the array antennas 23 in the radome 1 on the fuselage of the aeroplane.
  • twelve array antennas 23 having a vertically and b horizontally are arranged at a pitch of 30 degrees.
  • An elevation is at an angle ⁇ relative to the mounting plane.
  • Each array antenna 23 is divided into 6 x 4 blocks (not shown) and all of the 24 blocks are in-phase composed to produce the output of one array antenna 23.
  • the number, mounting angle, the number of divisions and the manner of divisions of the array antennas 23 may be changed depending on the directivity of the basic antenna element.
  • the antennas may be directed to the broadcasting satellite without regard to the number of apparatus by a simple circuit by using the navigation data derived from the inertial navigator the arrester bonded to the surface of the radome significantly affects to the transmittance of the electromagnetic wave in view of the positional relation with the antennas mounted in the radome, but the electromagnetic wave of the broadcasting satellite can be received at a very high level by in-phase composing the electromagnetic waves received by the plurality of antennas arranged in the radome.
  • the present apparatus uses the total electronic tracking system, the reliability is improved and the faster tracking is attained.
  • the electromagnetic wave of the broadcasting satellite can be stably received at all attitudes of the aeroplane.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Physics & Mathematics (AREA)
  • Remote Sensing (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Signal Processing (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
  • Details Of Aerials (AREA)
EP93309519A 1992-11-30 1993-11-29 Récepteur mobile pour signaux satellites radio diffusés Expired - Lifetime EP0600699B1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
JP4320445A JPH06169274A (ja) 1992-11-30 1992-11-30 衛星放送移動受信装置
JP320444/92 1992-11-30
JP320445/92 1992-11-30
JP32044492A JP3306758B2 (ja) 1992-11-30 1992-11-30 衛星放送移動受信装置

Publications (2)

Publication Number Publication Date
EP0600699A1 true EP0600699A1 (fr) 1994-06-08
EP0600699B1 EP0600699B1 (fr) 1999-05-06

Family

ID=26570089

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93309519A Expired - Lifetime EP0600699B1 (fr) 1992-11-30 1993-11-29 Récepteur mobile pour signaux satellites radio diffusés

Country Status (4)

Country Link
US (1) US5678171A (fr)
EP (1) EP0600699B1 (fr)
CA (1) CA2110205C (fr)
DE (1) DE69324771T2 (fr)

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FR2735304A1 (fr) * 1995-06-12 1996-12-13 Alcatel Espace Systeme de communication par satellites a defilement, satellite, station et terminal y inclus
GB2306055A (en) * 1995-10-06 1997-04-23 Roke Manor Research Improvements in or relating to antennas
WO1998029968A2 (fr) * 1996-12-30 1998-07-09 At & T Corp. Telephone portatif par satellite destine a des communications a liaison directe avec un satellite
WO1998029967A2 (fr) * 1996-12-30 1998-07-09 At & T Corp. Systeme de telecommunications a liaison directe avec un satellite
WO1998049745A1 (fr) * 1997-04-30 1998-11-05 Alcatel Systeme d'antennes, notamment pour pointage de satellites defilants
FR2764444A1 (fr) * 1997-06-09 1998-12-11 Alsthom Cge Alcatel Systeme d'antennes, notamment pour pointage de satellites defilants
FR2765751A1 (fr) * 1997-07-01 1999-01-08 Nec Corp Procede de capture/poursuite de satellite et appareil capable de reduire les charges de fonctionnemt d'une station terrestre
WO1999023769A1 (fr) * 1997-10-30 1999-05-14 Raytheon Company Communication sans fil utilisant un noeud de commutation aeroporte
EP0776102A3 (fr) * 1995-11-21 1999-09-01 Diehl Stiftung & Co. Procédé et dispositif pour l'échange d'informations entre stations
GB2402553A (en) * 2003-06-06 2004-12-08 Westerngeco Seismic Holdings Segmented antenna system for offshore radio networks and method of using the same
ITRM20110143A1 (it) * 2011-03-24 2012-09-25 Spacesys Di Giorgio Perrotta Procedimento di puntamento fra un'antenna di teminale mobile e un satellite e relativa apparecchiatura
EP3306749A4 (fr) * 2015-06-02 2018-12-26 Mitsubishi Electric Corporation Dispositif d'antenne

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US6661353B1 (en) 2001-03-15 2003-12-09 Matsushita Avionics Systems Corporation Method for displaying interactive flight map information
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FR2836607B1 (fr) * 2002-02-22 2004-05-28 Thales Sa Systeme antennaire pour liaisons entre vehicule mobile et objets aeriens
FR2838243B1 (fr) * 2002-04-09 2006-06-02 Thales Sa Systeme antennaire modulaire
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IL171450A (en) * 2005-10-16 2011-03-31 Starling Advanced Comm Ltd Antenna board
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US8917207B2 (en) * 2007-10-16 2014-12-23 Livetv, Llc Aircraft in-flight entertainment system having a multi-beam phased array antenna and associated methods
US8402268B2 (en) 2009-06-11 2013-03-19 Panasonic Avionics Corporation System and method for providing security aboard a moving platform
US8704960B2 (en) 2010-04-27 2014-04-22 Panasonic Avionics Corporation Deployment system and method for user interface devices
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US9755295B2 (en) * 2012-05-01 2017-09-05 Avago Technologies General Ip (Singapore) Pte. Ltd. Antenna configured for use in a wireless transceiver
CA2831325A1 (fr) 2012-12-18 2014-06-18 Panasonic Avionics Corporation Calibrage de systeme d'antenne
JP6313340B2 (ja) 2013-02-11 2018-04-18 ゴーゴー・エルエルシー モバイルプラットフォームのためのマルチプルアンテナシステムおよび方法
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KR101694261B1 (ko) * 2015-09-09 2017-01-23 현대자동차주식회사 안테나 장치 및 상기 안테나 장치를 이용하는 차량
FR3050978B1 (fr) * 2016-05-03 2019-09-06 Dassault Aviation Dispositif de support d'un equipement radioelectrique d'un aeronef, systeme radioelectrique et aeronef
FR3054934B1 (fr) * 2016-08-03 2019-07-05 Airbus Operations Systeme d'emission et/ou de reception d'ondes electromagnetiques embarque dans un aeronef
US10637135B2 (en) * 2017-05-09 2020-04-28 The Boeing Company Aircraft radome apparatuses and methods
FR3099001A1 (fr) * 2019-07-19 2021-01-22 Airbus Defence And Space Sas Aérodyne avec antenne et procédé d’agencement associé

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FR2735304A1 (fr) * 1995-06-12 1996-12-13 Alcatel Espace Systeme de communication par satellites a defilement, satellite, station et terminal y inclus
US5861840A (en) * 1995-10-06 1999-01-19 Roke Manor Research Limited Telecommunications antenna
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DE19543321B4 (de) * 1995-11-21 2006-11-16 Diehl Stiftung & Co.Kg Verfahren und Einrichtung zum drahtlosen Austausch von Informationen zwischen Stationen
EP0776102A3 (fr) * 1995-11-21 1999-09-01 Diehl Stiftung & Co. Procédé et dispositif pour l'échange d'informations entre stations
WO1998029967A3 (fr) * 1996-12-30 1998-09-11 At & T Corp Systeme de telecommunications a liaison directe avec un satellite
WO1998029968A3 (fr) * 1996-12-30 1998-09-11 At & T Corp Telephone portatif par satellite destine a des communications a liaison directe avec un satellite
WO1998029967A2 (fr) * 1996-12-30 1998-07-09 At & T Corp. Systeme de telecommunications a liaison directe avec un satellite
WO1998029968A2 (fr) * 1996-12-30 1998-07-09 At & T Corp. Telephone portatif par satellite destine a des communications a liaison directe avec un satellite
US5995041A (en) * 1996-12-30 1999-11-30 At&T Corp. Communication system with direct link to satellite
US6218999B1 (en) 1997-04-30 2001-04-17 Alcatel Antenna system, in particular for pointing at non-geostationary satellites
WO1998049745A1 (fr) * 1997-04-30 1998-11-05 Alcatel Systeme d'antennes, notamment pour pointage de satellites defilants
AU736121B2 (en) * 1997-04-30 2001-07-26 Alcatel An antenna system, in particular for pointing at non-geostationary satellites
FR2764444A1 (fr) * 1997-06-09 1998-12-11 Alsthom Cge Alcatel Systeme d'antennes, notamment pour pointage de satellites defilants
FR2765751A1 (fr) * 1997-07-01 1999-01-08 Nec Corp Procede de capture/poursuite de satellite et appareil capable de reduire les charges de fonctionnemt d'une station terrestre
US6061562A (en) * 1997-10-30 2000-05-09 Raytheon Company Wireless communication using an airborne switching node
WO1999023769A1 (fr) * 1997-10-30 1999-05-14 Raytheon Company Communication sans fil utilisant un noeud de commutation aeroporte
EP1826920A1 (fr) * 1997-10-30 2007-08-29 Raython Company Communication sans fil utilisant un noeud de commutation aéroporté
GB2402553A (en) * 2003-06-06 2004-12-08 Westerngeco Seismic Holdings Segmented antenna system for offshore radio networks and method of using the same
GB2402553B (en) * 2003-06-06 2007-06-20 Westerngeco Seismic Holdings A segmented antenna system for offshore radio networks and method of using the same
US7383151B2 (en) 2003-06-06 2008-06-03 Western Geco L.L.C. Segmented antenna system for offshore radio networks and method of using same
ITRM20110143A1 (it) * 2011-03-24 2012-09-25 Spacesys Di Giorgio Perrotta Procedimento di puntamento fra un'antenna di teminale mobile e un satellite e relativa apparecchiatura
EP3306749A4 (fr) * 2015-06-02 2018-12-26 Mitsubishi Electric Corporation Dispositif d'antenne

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DE69324771T2 (de) 1999-09-09
EP0600699B1 (fr) 1999-05-06
DE69324771D1 (de) 1999-06-10
US5678171A (en) 1997-10-14
CA2110205A1 (fr) 1994-05-31
CA2110205C (fr) 1999-11-23

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